基于飞/发性能一体化快速迭代的循环参数匹配  

Cycle Parameters Matching Design Based on Fast Iterative Aircraft/Engine Performance Integration

作　　者：曹铭栋 王昭 高靖俞 樊巍 刘兵 CAO Ming-dong;WANG Zhao;GAO Jing-yu;FAN Wei;LIU Bing(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500

出　　处：《航空发动机》2024年第1期35-43,共9页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：针对150 kN级大涵道比涡扇发动机总体性能参数匹配设计问题,以A340-300飞机对发动机的任务需求为例,采用基于飞/发性能一体化快速迭代优化方法,将飞机/发动机一体化设计与发动机总体性能优化设计进行耦合迭代,对多约束条件下的大涵道比涡扇发动机总体性能方案进行优化设计。结果表明:在保证发动机满足飞机任务需求和任务载荷要求,以及发动机尺寸、质量、污染排放要求等约束条件下,飞机的最大起飞质量较初始方案减轻约14.33%,较A340-300飞机的最大起飞质量减轻约8%~9%;燃油消耗量较初始方案减少约20.6%;在保证发动机与飞机良好匹配性的前提下,通过飞发优化迭代使发动机和飞机的设计难度都有一定程度地降低。采用的研究思路与方法是合理、可行的,具有工程实用价值。Aiming at the overall performance parameters matching design for a 150kN class high bypass ratio turbofan engine,taking the mission requirements of A340-300 aircraft as an example,a fast iterative optimization method based on aircraft/engine performance integration is adopted to couple and iterate the aircraft/engine integration design and engine overall performance design,thus to optimize the design of the overall performance scheme for high bypass ratio turbofan engine with multiple constraints.The results show that when the engines meet the mission and payload requirements of the aircraft,as well as constraints in terms of size,weight,and emission,the maximum take-off weight of the aircraft is reduced by 14.33%,and about 8%-9%lower compared with the actual maximum take-off weight of A340-300 aircraft;the fuel consumption is about 20.6%lower than that of the original scheme.On the premise of ensuring a good match between the engine and the aircraft,the design difficulty of both the engine and the aircraft is reduced to a certain extent through iterative optimization of the aircraft/engine integration.The ideas and methods are reasonable,feasible,and have practical engineering value.

关 键 词：大涵道比涡扇发动机 飞/发性能一体化 快速迭代 耦合迭代 总体性能参数 优化 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]